Abstract

This paper presents an attempt to control the laminar-turbulent transition on a swept wing in supersonic flow. The first part deals with the control of the transition due to crossflow (CF) instabilities present on a swept wing, by using Micron-Sized Roughness elements (MSR); the second one
is focused on the prevention of the turbulent contamination along the Leading Edge (LE), using appropriate Anti-Contamination Devices (ACD). The work includes both numerical and experimental investigation.